Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:
Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
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![Example 10.1
A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge
M2
(Fig. 10E.1). An oblique shock, making an angle of 40° with the flow P= 20 kPa
T=-10 °C
0=40%
direction, is attached to the wedge under these flow conditions. If the static
M 2.0
pressure and temperature in the uniform flow are, respectively, 20 kPa and
-10 °C, determine the static pressure and temperature behind the wave, the
Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F8594afb5-55c6-47a0-bb69-07fb5ffafa94%2Feb7b916d-360d-4b46-ad73-29c184a6a1e7%2F83779fi_processed.jpeg&w=3840&q=75)
Transcribed Image Text:Example 10.1
A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge
M2
(Fig. 10E.1). An oblique shock, making an angle of 40° with the flow P= 20 kPa
T=-10 °C
0=40%
direction, is attached to the wedge under these flow conditions. If the static
M 2.0
pressure and temperature in the uniform flow are, respectively, 20 kPa and
-10 °C, determine the static pressure and temperature behind the wave, the
Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:
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